Gas turbine, gas-turbine control device, and gas turbine operation method

Abstract

A gas turbine equipped with a compressor, a combustion chamber and a turbine is further equipped with: a pressurizing device for taking a portion of the compressed air compressed by the compressor, and pressurizing the compressed air; a combustion chamber cooling line for cooling the combustion chamber using the pressurized compressed air; a temperature regulating line for regulating the temperature of a stationary member of a blade ring or the like of a turbine by using the pressurized compressed air; a combustion chamber supply line through which the compressed air flows from the pressurizing device to the combustion chamber cooling line; a turbine supply line through which the compressed air flows from the pressurizing device to the temperature regulating line; a heater for heating the compressed air, provided in the turbine supply line; and a control device capable of controlling the heater.

The invention claimed is: 
     
       1. A gas turbine configured to acquire rotational power by supplying fuel to a combustion chamber and burning the fuel in compressed air compressed by a compressor, and supplying generated combustion gas to a turbine, the gas turbine comprising:
 means for pressurizing a portion of the compressed air compressed by the compressor, the portion of the compressed air having flowed into the means for pressurizing; 
 means for cooling the combustion chamber with at least a first part of the portion of the compressed air pressurized by the means for pressurizing; 
 means for regulating turbine temperature to regulate a temperature of a stationary member of the turbine with at least a second part of the portion of the compressed air pressurized by the means for pressurizing; 
 a pressurization supply channel through which the portion of the compressed air is configured to flow from the compressor to the means for pressurizing; 
 a combustion chamber supply channel through which at least the first part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for cooling the combustion chamber; 
 a turbine supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for regulating turbine temperature; 
 means for cooling at least the first part of the portion of the compressed air, the means for cooling at least the first part of the portion of the compressed air being provided in the combustion chamber supply channel; 
 means for heating at least the second part of the portion of the compressed air, the means for heating the at least the second part of the portion of the compressed air being provided in the turbine supply channel; 
 a connecting supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for regulating turbine temperature to the means for cooling the combustion chamber; 
 a control device capable of controlling at least one of the means for cooling at least the first part of the portion of the compressed air and the means for heating at least the second part of the portion of the compressed air; 
 a first flow rate regulating mechanism provided in the turbine supply channel; 
 a second flow rate regulating mechanism provided in the pressurization supply channel; 
 a third flow rate regulating mechanism provided in the combustion chamber supply channel; and 
 a fourth flow rate regulating mechanism provided in the connecting supply channel; 
 wherein the control device is configured to control the first flow rate regulating mechanism to regulate a flow rate of at least the second part of the portion of the compressed air flowing into the means for regulating turbine temperature, control the second flow rate regulating mechanism to regulate a flow rate of the portion of the compressed air flowing into the means for pressurizing, control the third flow rate regulating mechanism to regulate a flow rate of at least the first part of the portion of the compressed air flowing into the means for cooling the combustion chamber, and control the fourth flow rate regulating mechanism to regulate a flow rate of at least the second part of the portion of the compressed air flowing from the means for regulating turbine temperature into the means for cooling the combustion chamber. 
 
     
     
       2. The gas turbine according to  claim 1 , wherein:
 the stationary member includes a blade ring; 
 the means for regulating turbine temperature includes a blade ring inner channel defined in the blade ring; and 
 the connecting supply channel is configured to pass at least the second part of the portion of the compressed air to the means for cooling the combustion chamber from the blade ring inner channel defined in the blade ring at a rated operation of the gas turbine. 
 
     
     
       3. The gas turbine according to  claim 1 , wherein:
 the control device is configured to control the first flow rate regulating mechanism to close the turbine supply channel, so as to block supply of at least the second part of the portion of the compressed air to the means for regulating turbine temperature. 
 
     
     
       4. The gas turbine according to  claim 1 , wherein:
 the first flow rate regulating mechanism includes at least one of: 
 an on-off valve configured to open and close the turbine supply channel; and 
 a flow rate regulating valve configured to regulate the flow rate of at least the second part of the portion of the compressed air flowing through the turbine supply channel. 
 
     
     
       5. The gas turbine according to  claim 1 , further comprising:
 means for cooling the portion of the compressed air, the means for cooling the portion of the compressed air being provided in the pressurization supply channel. 
 
     
     
       6. The gas turbine according to  claim 1 , wherein:
 the control device is configured to control at least one of the means for cooling at least the first part of the portion of the compressed air and the means for heating at least the second part of the portion of the compressed air during a startup operation of the gas turbine so that the combustion chamber is cooled by the means for cooling the combustion chamber and the stationary member of the turbine is heated by the means for regulating turbine temperature; 
 and the control device is further configured to control at least one of the means for cooling at least the first part of the portion of the compressed air and the means for heating at least the second part of the portion of the compressed air during a rated operation of the gas turbine so that the combustion chamber is cooled by the means for cooling the combustion chamber and the stationary member of the turbine is cooled by the means for regulating turbine temperature. 
 
     
     
       7. A gas turbine with a control device configured to control an operation of the gas turbine which is configured to acquire rotational power by supplying fuel to a combustion chamber and burning the fuel in compressed air compressed by a compressor and supplying generated combustion gas to a turbine, the gas turbine including:
 means for pressurizing a portion of the compressed air compressed by the compressor, the portion of the compressed air having flowed into the means for pressurizing; 
 means for cooling the combustion chamber with at least a first part of the portion of the compressed air pressurized by the means for pressurizing; 
 means for regulating turbine temperature to regulate a temperature of a stationary member of the turbine with at least a second part of the portion of the compressed air pressurized by the means for pressurizing; 
 a combustion chamber supply channel through which at least the first part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for cooling the combustion chamber; 
 a turbine supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for regulating turbine temperature; 
 means for heating at least the second part of the portion of the compressed air, the means for heating at least the second part of the portion of the compressed air being provided in the turbine supply channel; 
 a connecting supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for regulating turbine temperature to the means for cooling the combustion chamber; and 
 a flow rate regulating mechanism provided in the connecting supply channel; 
 wherein, in a rated operation mode, which is a control mode during rating of the gas turbine, the control device is configured to control the flow rate regulating mechanism to cause at least the second part of the portion of the compressed air to flow from the means for regulating turbine temperature into the means for cooling the combustion chamber. 
 
     
     
       8. The gas turbine with the control device according to  claim 7 , further comprising:
 means for cooling at least the first part of the portion of the compressed air, 
 the means for cooling at least the first part of the portion of the compressed air being provided in the combustion chamber supply channel, 
 wherein an operation method for the gas turbine with the control device comprises: 
 a startup operation of the gas turbine to cool the combustion chamber by the means for cooling the combustion chamber and to heat the stationary member of the turbine by the means for regulating turbine temperature during the startup operation of the gas turbine; and 
 the rated operation mode of the gas turbine to cool the combustion chamber by the means for cooling the combustion chamber and to cool the stationary member of the turbine by the means for regulating turbine temperature during the rated operation mode of the gas turbine. 
 
     
     
       9. An operation method for a gas turbine configured to acquire rotational power by supplying fuel to a combustion chamber and burning the fuel in compressed air compressed by a compressor and supplying generated combustion gas to a turbine, the gas turbine including:
 means for pressurizing a portion of the compressed air compressed by the compressor, the portion of the compressed air having flowed into the means for pressurizing; 
 means for cooling the combustion chamber with at least a first part of the portion of the compressed air pressurized by the means for pressurizing; 
 means for regulating turbine temperature to regulate a temperature of a stationary member of the turbine with at least a second part of the portion of the compressed air pressurized by the means for pressurizing; 
 a combustion chamber supply channel through which at least the first part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for cooling the combustion chamber; 
 a turbine supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for regulating turbine temperature; 
 means for heating at least the second part of the portion of the compressed air, the means for heating at least the second part of the portion of the compressed air being provided in the turbine supply channel; 
 a connecting supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for regulating turbine temperature to the means for cooling the combustion chamber; and 
 a flow rate regulating mechanism provided in the connecting supply channel; 
 wherein: 
 in a rated operation of the gas turbine, the flow rate regulating mechanism is controlled to cause at least the second part of the portion of the compressed air to flow from the means for regulating turbine temperature into the means for cooling the combustion chamber; 
 the stationary member includes a blade ring; 
 the means for regulating turbine temperature includes a blade ring inner channel defined in the blade ring; and 
 the connecting supply channel is configured to pass at least the second part of the portion of the compressed air to the means for cooling the combustion chamber from the blade ring inner channel defined in the blade ring at the rated operation of the gas turbine. 
 
     
     
       10. The operation method for the gas turbine according to  claim 9 , wherein:
 the gas turbine further includes means for cooling at least the first part of the portion of the compressed air, the means for cooling at least the first part of the portion of the compressed air being provided in the combustion chamber supply channel; 
 and the operation method for the gas turbine includes: 
 a startup operation of the gas turbine to cool the combustion chamber by the means for cooling the combustion chamber and to heat the stationary member of the turbine by the means for regulating turbine temperature during the startup operation of the gas turbine; 
 and the rated operation of the gas turbine to cool the combustion chamber by the means for cooling the combustion chamber and to cool the stationary member of the turbine by the means for regulating turbine temperature during the rated operation of the gas turbine.